Ongoing research is presented directed toward the development of a Mach-scaled rotor model with piezoelectric bender-actuated trailing-edge flaps for individual blade control of helicopter vibration. First, an analytical model is developed for the coupled actuator-flap-rotor dynamic response in hover. Then, the analysis is validated by using test data obtained by hover testing a 6-ft (1.82-m)-diam, Froude-scaled rotor with piezo-bender-actuated trailing-edge flaps. The analytic model shows good correlation with experimental lap deflections and oscillatory hub loads. For the Froude-scaled model flap deflections of +/-4 to +/-8 deg, for 1 to 5 /rev flap excitation, were achieved at 900 rpm. This flap activation resulted in a 10% variation in the steady rotor thrust level at 6 deg collective. Next, two Mach-scaled rotor blades with piezo-bender actuation were designed and fabricated. The rotor was tested in the vacuum chamber, and flap deflections of +/-8 deg were achieved in vacuum at the Mach-scaled operating speed of 2000 rpm. The analysis predicts that in hover flap deflections of +/-5 deg can be achieved at 2000 rpm. Future work will involve hover tests followed by forward flight tests in the wind tunnel to confirm these predictions and demonstrate concept feasibility.


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    Titel :

    Analysis and testing of mach-scaled rotor with trailing-edge flaps


    Weitere Titelangaben:

    Modellierung und Test eines bezüglich der Mach-Zahl maßstabsgetreuen Drehflügels mit einem Piezoaktuator zur Schwingungsdämpfung


    Beteiligte:
    Koratkar, N.A. (Autor:in) / Chopra, I. (Autor:in)

    Erschienen in:

    AIAA Journal ; 38 , 7 ; 1113-1124


    Erscheinungsdatum :

    2000


    Format / Umfang :

    12 Seiten, 28 Bilder, 1 Tabelle, 24 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch